EP3659923A1 - Propulsion system of an aircraft comprising a movable and hinged cover - Google Patents

Propulsion system of an aircraft comprising a movable and hinged cover Download PDF

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Publication number
EP3659923A1
EP3659923A1 EP19203914.7A EP19203914A EP3659923A1 EP 3659923 A1 EP3659923 A1 EP 3659923A1 EP 19203914 A EP19203914 A EP 19203914A EP 3659923 A1 EP3659923 A1 EP 3659923A1
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EP
European Patent Office
Prior art keywords
coils
outer cover
series
cover
translation
Prior art date
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Granted
Application number
EP19203914.7A
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German (de)
French (fr)
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EP3659923B1 (en
Inventor
Pierre Charon
Frédéric JOURNADE
Laurent CAZEAUX
Pascal Gougeon
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Airbus Operations SAS
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Airbus Operations SAS
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Publication of EP3659923A1 publication Critical patent/EP3659923A1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/08—Inspection panels for power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/404—Suspension arrangements specially adapted for supporting vertical loads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/766—Control or regulation of thrust reversers with blocking systems or locking devices; Arrangement of locking devices for thrust reversers

Definitions

  • the present invention relates to a propulsion system of an aircraft which comprises a movable and articulated hood, a method for placing such a propulsion system in the maintenance position, as well as an aircraft comprising at least one such propulsion system.
  • An aircraft conventionally comprises at least one propulsion system which comprises an engine forming a core around which are arranged a fixed internal structure (also called IFS "Internai Fixed Structure” in English) surrounding the engine, and external cowls arranged around the fixed internal structure.
  • a fixed internal structure also called IFS "Internai Fixed Structure” in English
  • the invention provides an alternative propulsion system which comprises a movable and articulated outer cover which can be moved in translation with the fixed internal structure for maintenance operations.
  • an aircraft propulsion system is proposed as claimed in claim 1.
  • Such a propulsion system thus makes it possible, during maintenance operations, to move the outer cover and the fixed internal structure towards the rear and therefore at a distance from the front covers in order to release the engine.
  • an aircraft 10 comprises a fuselage 12 on each side of which is fixed a wing 14 which carries at least one propulsion system 100 comprising a turbofan 150 and a mast 152 which secures the turbofan 150 under the wing 14 .
  • X is called the longitudinal axis of the turbofan 150 which is parallel to the longitudinal axis of the aircraft 10 and oriented positively towards the front of the aircraft 10, Y the transverse axis which is horizontal when the aircraft 10 is on the ground, and Z the vertical axis when the aircraft 10 is on the ground, these three axes X, Y and Z being orthogonal to one another.
  • the figure 2 schematically shows the propulsion system 100 which comprises the turbofan 150 and the mast 152 and the figure 3 shows a schematic side view of the double-flow turbojet 150.
  • the turbojet 150 comprises a motor 156 with a blower 151 intended to generate an air flow in the turbojet 150 in a direction of movement 50 of the air in the turbojet 150, where in known manner, the air flow moves then downstream of the fan 151 partly in a primary stream 153 of the turbojet 150 and partly in a secondary stream 154 of the turbojet 150.
  • the engine 156 forms a core through which the air from the primary stream 153 circulates and comprising in series an engine compressor, a combustion chamber and an engine turbine.
  • the fan 151 is at the front of the engine 156.
  • the motor 156 is surrounded by a fixed internal structure 158 (also called IFS “Internai Fixed Structure” in English) which internally delimits the secondary vein 154.
  • the fixed internal structure 158 consists of two internal cowls 159 arranged on one side and on the other side of the mid-plane XZ of the turbojet engine 150.
  • Each internal cover 159 here comprises a central part 159a taking the form of a half-cylinder whose axis is the longitudinal axis X, and two extensions 159b-c.
  • Each 159b-c extension generally takes the form of a plate where each extends in a plane generally parallel to the middle plane XZ.
  • the upper extension 159b extends upwards from the upper edge of the central part 159a and the lower extension 159c extends downwards from the lower edge of the central part 159a.
  • the turbojet engine 150 In the operating position of the turbojet engine 150, the fixed internal structure 158, that is to say the internal cowls 159, are fixed relative to the engine 156, and in the maintenance position the fixed internal structure 158, that is to say -to say the internal covers 159, are free with respect to the engine 156.
  • the turbojet engine 150 comprises locking means 180 which can alternately take a locking position in which they lock the internal covers 159 to the engine 156, and a unlocking position in which they release the internal covers 159 of the motor 156.
  • the turbojet engine 150 also includes a nacelle 160 which surrounds the fixed internal structure 158 and which comprises a fan casing 162 around the fan 151 and two external covers 164 arranged around the fixed internal structure 158, that is to say internal covers 159.
  • the external covers 164 are also arranged on either side of the middle plane XZ of the turbojet engine 150. Each external cover 164 is located around one of the internal covers 159.
  • the fan casing 162 is fixed and at the front of the nacelle 160 while each outer cover 164 is at the rear of the fan casing 162 and is movable in translation in a direction of translation generally parallel to the longitudinal axis X
  • the fan casing 162 also consists of two fan cowls arranged on either side of the middle plane XZ of the turbojet engine 150.
  • the figure 3 shows the turbojet engine 150 with the outer covers 164 in a forward position
  • the figure 4 shows the turbojet 150 with the outer covers 164 in a retracted position.
  • the outer covers 164 externally delimit the secondary vein 154.
  • Each outer cover 164 is slidably mounted parallel to the direction of translation on the corresponding inner cover 159 by means of a high slide link 170 and a low slide link 172.
  • the high slide link 170 is arranged in the upper part of the turbojet 150 and the lower slide link 172 is arranged in the lower part of turbojet 150.
  • the upper slide link 170 and the low slide link 172 are produced by any suitable means such as for example a groove in one of the external cover 164 or the internal cover 159 and a slide integral with the other among the internal cover 159 or the outer cover 164 and which slides in the groove.
  • the upper slide link 170 and the low slide link 172 are more particularly implemented at the upper extension 159b and the lower extension 159c.
  • Each outer cover 164 is also slidably mounted parallel to the direction of translation on the mast 152 by means of an upper slide link 174 also arranged in the upper part of the turbojet engine 150.
  • the upper slide link 174 comprises, on the one hand, a beam 176 having a groove and, on the other hand, at least one slide secured to the outer cover 164 which slides in the groove.
  • the beam 176 is fixed to the mast 152 by means of a pivot link around an axis of rotation 177 generally parallel to the direction of translation and therefore here to the longitudinal axis X, thus forming a hinge allowing the movement of the outer cover 164 between a closed position in which the outer cover 164 is tightened around the motor 156 and an open position in which the outer cover 164 is moved away from the motor 156 by driving the corresponding inner cover 159.
  • the two outer covers 164 are tightened to form an aerodynamic continuity with the fan casing 162.
  • the turbojet 150 also includes an inverter system 250.
  • the reversing system 250 comprises the outer covers 164 which are movable in translation relative to the motor 156 between an advanced position and a retracted position. In the advanced position, the outer covers 164 are attached to the rear of the fan casing 162 and in the retracted position, the two outer covers 164 are spaced from the fan casing 162 to open a window 252 between the secondary stream 154 and the outside.
  • the window 252 is delimited at the front by the fan casing 162 and at the rear by the external covers 164 as can be seen on the figure 4 .
  • the turbojet engine 150 comprises a first mechanical transmission system which includes, for example actuators such as jacks, motors, racks and which is controlled by a control unit of the aircraft 10.
  • a first mechanical transmission system at the level of the lower slide link 172 and one at the level of the upper slide link 174.
  • the reversing system 250 also includes at least one door 254 which is mounted to rotate on the outer cover 164 around an axis generally perpendicular to the longitudinal axis X.
  • Each door 254 is movable between a retracted position and a deployed position.
  • the door 254 In the retracted position ( figure 3 ), the door 254 is not across the secondary stream 154 and therefore does not obstruct the passage of the air flow in the secondary stream 154.
  • the deployed position ( figure 4 ) the door 254 is across the secondary stream 154 so as to divert the air flow towards the window 252.
  • the door 254 comes against the internal cover 159.
  • the reversing system 250 also includes a second mechanical transmission system 256 which makes it possible to move the door 254 from the retracted position to the deployed position when the outer cover 164 changes from the advanced position to the retracted position.
  • the second mechanical transmission system 256 is a rod fixed between the door 254 and the fixed internal structure 158, but it could for example include actuators such as jacks, motors controlled by the control unit.
  • the turbojet engine 150 comprises cascades 256 which are fixed to the outer cover 164 by means of belt means 258 which can alternately assume a belt position in which they lock the cascades 256 to the outer cover 164, and a disengagement position in which they release the cascades 256 from the outer cover 164.
  • the cascades 256 are positioned under the fan casing 162 and in the retracted position, the cascades 256 are positioned across the window 252.
  • the displacement in translation of the cascades 256 between the advanced position and the retracted position is also ensured by the upper slide link 174, where the cascades 256 comprise at least one slide which slides in the groove of the beam 176.
  • the Figures 5 and 6 correspond to the maintenance phases of the turbojet 150. From the advanced position ( figure 5 ), the locking means 180 are unlocked and the belt means 258 are disengaged, that is to say that the internal covers 159 are released from the motor 156 and that the cascades 256 are released from the external cover 164.
  • the internal covers 159 By passing the outer covers 164 from the advanced position to the retracted position ( figure 6 ), the internal covers 159 also move backwards while the cascades 256 remain under the fan casing 162. This makes it possible to free access to the engine 156 without it being necessary to remove the various covers 159 and 164 .
  • Each fan cover is also here attached to the mast 152 by means of a pivot connection around the axis of rotation 177.
  • the pivot connection is produced by any suitable means such as for example hinges.
  • the locking means 180 comprise, on the one hand, a groove which is open towards the outside, that is to say radially with respect to the longitudinal axis and the direction of translation, which extends around the motor 156 and which is integral therewith, and, on the other hand, for each internal cover 159, a rib secured to the internal cover 159 which accommodates in the groove in the locked position and in comes out in unlocked position.
  • the rib which is in the groove prevents the displacement of the internal covers 159 parallel to the direction of translation. The exit of the rib from the groove is achieved by lifting the rib relative to the groove.
  • the belt means 258 comprise, on the one hand, a groove which is open towards the outside, that is to say radially with respect to the longitudinal axis and the direction of translation, which extends around the motor 156 and which is secured to the outer cover 164, and, on the other hand, for each cascade 256, a rib secured to the cascade 256 which lodges in the groove in the belt position and leaves it in the disengagement position.
  • the rib which is in the groove makes it possible to secure the cascade 256 and the outer cover 164 to ensure the movements parallel to the direction of translation.
  • the exit of the rib from the groove is achieved by lowering the groove towards the motor 156 relative to the rib.
  • the figure 7 shows the beam 176 mounted on the mast 152 with its groove 702 and a slide 704 of the outer cover 164 which slides in the groove 702 parallel to the direction of translation.
  • the figure 8 shows a front view of the beam 176 where each slide 704 of the outer cover 164 has a degree of freedom in translation parallel to the direction of translation, as well as a degree of freedom in rotation about a flapping axis 802 parallel to the direction of translation and different from the axis of rotation 177. That is to say that between each slide 704 of the outer cover 164 and the groove 702, there is a sliding pivot connection.
  • the angular movement (double arrow 804) of the corresponding pivot link is limited, it is for example of the order of +/- 4 degrees.
  • the angular movement is sufficient to allow the disengagement of the belt means 258 by leaving the rib from the groove.
  • the method for placing the propulsion system 100 in the maintenance position that is to say for moving the outer cover 164 and the inner cover 159 backwards to make room for a technician working on the engine 156 consists of: 'first to unlock the first locking means 180 and the belt means 258.
  • This process applies to each side of the turbojet 150.
  • the slide 704 has a bean section and it is housed in a groove 702 also having a bean section but with larger dimensions.
  • the slide 704 and the groove 702 can have other cross-sectional shapes such as for example a circular section. It is sufficient that the dimensions of the groove 702 are greater than the dimensions of the slider 704 to allow the rotation of the sliding pivot connection.
  • the bottom of the groove 702 is covered with a profile 806 in particular metallic and more particularly aluminum.
  • This profile 806 makes it possible to improve the sliding of the slide 704 and to reinforce the beam 176.
  • the interior surface of the profile 806 in contact with the slide 806 can be covered with a sliding coating.
  • the first mechanical transmission system can comprise, for example, actuators such as jacks, motors, etc.
  • the figure 9 shows a particular embodiment of the first mechanical transmission system 900 which consists of a synchronous linear electric motor 902 and which is put in place at the level of the upper slide link 174.
  • a linear electric motor 902 can also be implemented place at the level of the lower slide link 172 where the beam constitutes a part of the internal cover 159 and the slide constitutes a part of the external cover 164.
  • Each linear electric motor 902 comprises a first series of coils 906a-c aligned one after the other in the direction of translation.
  • Each linear electric motor 902 comprises a second series of coils 908a-c aligned one after the other in the direction of translation.
  • Each coil 908a-c of the second series is opposite a coil 906a-c of the first series.
  • Each beam 176 has a recess 901 which extends parallel to the direction of translation and in which are housed the first series of coils 906a-c and the second series of coils 908a-c.
  • Each linear electric motor 902 also comprises a strip 904 which is integrated into the slide 704 and which extends in the direction of translation and which consists of a succession of permanent magnets 910a-c aligned one after the other according to the direction of translation.
  • Permanent magnets 910a-c are placed between the first series and the second series of coils 906a-c, 908a-c.
  • the permanent magnets 910a-c present their North Pole alternately towards the first series of coils 906a-c and the second series of coils 908a-c.
  • the coils of said series are fixed on a support plate 914, 916 which is arranged on the side opposite to the slide 704.
  • the principle consists in supplying the coils 906a-c and 908a-c of each series which are opposite the permanent magnets 910a-c, with alternating current and judiciously phase-shifted, in order to generate a force causing the displacement of the slide 704.
  • Two coils are facing (that is to say a coil 906a-c of the first series facing a coil 908a-c of the second series) are supplied in an identical manner and therefore calibrated in an identical manner.
  • each first mechanical transmission system 900 comprises a position sensor 912 which picks up the position of the slide 704 along the direction of translation and therefore the position of the permanent magnets 910a-c relative to the coils 906a-c, 908a -vs.
  • the position sensor 912 is for example a magnetic sensor which detects the change of magnetic field when the permanent magnets 910a-c pass and therefore the distance traveled by the slide 704. From the information delivered by the position sensor 912, the control unit determines the coils 906a-c, 908a-c which are opposite a permanent magnet 910a-c.
  • An electrical supply is provided to supply each coil 906a-c, 908a-c and it is controlled by the control unit as a function of the information delivered by the position sensor 912 so as to supply only the coils 906a-c, 908a-c which are opposite a permanent magnet 910a-c.
  • the selective supply of the coils 906a-c, 908a-c makes it possible to move the slider 704 along the direction of translation.
  • Each slide 704 can comprise a metal portion (consisting of a simple conductive plate or of parallel strands between them, arranged perpendicular to the path of the slide, and connected to the ends) without a magnet in the extension of the strip 904 to benefit from the currents of Eddy generated during movement of the slide 704 and thus ensure braking of the slide 704 at the end of the stroke.
  • the first mechanical transmission system 900 of the upper slide link 174 also includes a wedging system 950 which can alternately assume a wedging position in which the wedging system 950 blocks the two sets of coils 906a-c, 908a-c, preventing any movement of said coils 906a-c, 908a-c, and a free position in which the timing system 950 does not block the two series of coils 906a-c, 908a-c, allowing a rotary movement of said coils 906a-c, 908a -c around the axis of flap 802.
  • This wedging system 950 thus makes it possible to release the movement of the outer cover 164 around the flap axis 802.
  • the wedging system 950 comprises deformable pads 952 here two in number, for example made of elastomer, and arranged between a series of coils, here the second series of coils 908a-c, and the beam 176.
  • the deformable pads 952 are more precisely arranged between the support plate 916 and the beam 176.
  • the timing system 950 also includes pressurizing means 954 which are arranged opposite the deformable pads 952 against the other series of coils, here the first series of coils 906a-c.
  • the pressurizing means 954 can alternately take a pressure position in which they press on said other series of coils, to crush the deformable pads 952, or a release position in which they do not press on said other series of coils , so as to release the deformable pads 952.
  • the pressurizing means 954 may for example be clamping screws or electro-actuators such as electromagnets, jacks, etc.
  • the synchronous electric motor can be replaced by an asynchronous motor.
  • the orientation of the direction of translation will depend on the size around the propulsion system 100.
  • the direction of translation may have an angle close to 90 ° relative to the vertical axis Z to keep the fan casing 162 and the outer cover 164 aligned in the retracted position.
  • the direction of translation could have an angle close to 90 ° relative to the transverse axis Y to escape the wing of the aircraft 10 during deployment.
  • control unit comprises, connected by a communication bus: a processor or CPU (“Central Processing Unit” in English); a random access memory RAM (“Random Access Memory” in English); a read only memory (ROM); a storage unit such as a hard disk or a storage medium reader, such as an SD card reader (“Secure Digital” in English); at least one communication interface, allowing for example the control unit to communicate with the power supply, the position sensor 912, the mechanical transmission systems.
  • processor or CPU Central Processing Unit
  • RAM Random Access Memory
  • ROM read only memory
  • storage unit such as a hard disk or a storage medium reader, such as an SD card reader (“Secure Digital” in English
  • SD card reader Secure Digital
  • the processor is capable of executing instructions loaded into RAM from the ROM, an external memory (not shown), a storage medium (such as an SD card), or a network of communication.
  • the processor is able to read and execute instructions from RAM.
  • These instructions form a computer program causing the processor to implement all or part of the algorithms and steps described above.
  • All or part of the algorithms and steps described below can be implemented in software form by execution of a set of instructions by a programmable machine, for example a DSP (“Digital Signal Processor” in English) or a microcontroller, or be implemented in hardware form by a dedicated machine or component, for example an FPGA ("Field-Programmable Gate Array” in English) or an ASIC ("Application-Specific Integrated Circuit” in English).
  • a programmable machine for example a DSP (“Digital Signal Processor” in English) or a microcontroller
  • a dedicated machine or component for example an FPGA ("Field-Programmable Gate Array" in English) or an ASIC (“Application-Specific Integrated Circuit” in English).

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un système de propulsion (100) comportant un turboréacteur double flux (150) et un mât (152), où le turboréacteur (150) comporte un moteur (156), deux capots internes (159), et deux capots extérieurs (164), des premiers moyens de verrouillage pour verrouiller les capots internes (159) au moteur (156), des cascades (256) qui sont fixées au capot extérieur (164) par l'intermédiaire de moyens de ceinturage (258), où les capots extérieurs (164) sont mobiles en translation par rapport au moteur (156), où chaque capot extérieur (164) est coulissant parallèlement à une direction de translation sur un capot interne (159) par l'intermédiaire d'une liaison glissière haute (170) et d'une liaison glissière basse (172) et où chaque capot extérieur (164) est monté coulissant parallèlement à la direction de translation sur le mât (152) par l'intermédiaire d'une liaison glissière supérieure (174).Un tel système de propulsion permet ainsi lors des opérations de maintenance de déplacer le capot extérieur et la structure interne fixe vers l'arrière et donc à distance des capots avant afin de dégager le moteur.The invention relates to a propulsion system (100) comprising a turbofan (150) and a mast (152), where the turbojet (150) comprises a motor (156), two internal cowls (159), and two external cowls. (164), first locking means for locking the internal covers (159) to the motor (156), cascades (256) which are fixed to the external cover (164) by means of belt means (258), where the outer covers (164) are movable in translation relative to the motor (156), where each outer cover (164) is sliding parallel to a direction of translation on an inner cover (159) by means of a high sliding link (170) and a lower slide link (172) and where each outer cover (164) is slidably mounted parallel to the direction of translation on the mast (152) via an upper slide link (174). Such a propulsion system thus makes it possible during displacement maintenance operations cer the outer cover and the fixed internal structure towards the rear and therefore at a distance from the front covers in order to release the engine.

Description

La présente invention concerne un système de propulsion d'un aéronef qui comporte un capot mobile et articulé, un procédé pour placer un tel système de propulsion en position de maintenance, ainsi qu'un aéronef comportant au moins un tel système de propulsion.The present invention relates to a propulsion system of an aircraft which comprises a movable and articulated hood, a method for placing such a propulsion system in the maintenance position, as well as an aircraft comprising at least one such propulsion system.

Un aéronef comporte classiquement au moins un système de propulsion qui comporte un moteur formant un noyau autour duquel sont agencés une structure interne fixe (également appelée IFS « Internai Fixed Structure » en Anglo-saxon) entourant le moteur, et des capots extérieurs disposés autour de la structure interne fixe.An aircraft conventionally comprises at least one propulsion system which comprises an engine forming a core around which are arranged a fixed internal structure (also called IFS "Internai Fixed Structure" in English) surrounding the engine, and external cowls arranged around the fixed internal structure.

Lors des opérations de maintenance du système de propulsion, il est nécessaire d'ouvrir les capots extérieurs afin d'accéder au moteur. Mais comme l'accès est souvent limité et ne permet pas certaines opérations nécessitant des manipulations, il est alors nécessaire de démonter les capots extérieurs pour les déposer au sol afin de pouvoir également démonter la structure interne fixe et ainsi accéder au moteur.During maintenance operations on the propulsion system, it is necessary to open the exterior covers in order to gain access to the engine. But since access is often limited and does not allow certain operations requiring manipulation, it is then necessary to dismantle the outer covers to place them on the ground so that the fixed internal structure can also be dismantled and thus access the engine.

De telles opérations sont relativement longues et pénibles, car il faut démonter et déplacer des pièces relativement lourdes.Such operations are relatively long and painful, because it is necessary to disassemble and move relatively heavy parts.

Il existe un besoin de proposer un système de propulsion d'un aéronef qui comporte un capot extérieur qui peut être déplacé en translation vers l'arrière de la nacelle pour les opérations de maintenance.There is a need to propose a propulsion system for an aircraft which comprises an outer cover which can be moved in translation towards the rear of the nacelle for maintenance operations.

La demande de brevet US2013/277454 décrit un système de propulsion selon le préambule de la revendication 1 qui répond à ce besoin.The patent application US2013 / 277454 describes a propulsion system according to the preamble of claim 1 which meets this need.

L'invention propose un système de propulsion alternatif qui comporte un capot extérieur mobile et articulé qui peut être déplacé en translation avec la structure interne fixe pour les opérations de maintenance. A cet effet, est proposé un système de propulsion d'un aéronef tel que revendiqué dans la revendication 1.The invention provides an alternative propulsion system which comprises a movable and articulated outer cover which can be moved in translation with the fixed internal structure for maintenance operations. To this end, an aircraft propulsion system is proposed as claimed in claim 1.

Un tel système de propulsion permet ainsi, lors des opérations de maintenance, de déplacer le capot extérieur et la structure interne fixe vers l'arrière et donc à distance des capots avant afin de dégager le moteur.Such a propulsion system thus makes it possible, during maintenance operations, to move the outer cover and the fixed internal structure towards the rear and therefore at a distance from the front covers in order to release the engine.

Les caractéristiques de l'invention mentionnées ci-dessus, ainsi que d'autres, apparaîtront plus clairement à la lecture de la description suivante d'un exemple de réalisation, ladite description étant faite en relation avec les dessins joints, parmi lesquels :

  • La figure 1 est une vue de côté d'un aéronef selon l'invention,
  • La figure 2 est une représentation schématique en vue de face d'un système de propulsion selon l'invention,
  • La figure 3 est une vue en coupe de côté d'un turboréacteur du système de propulsion selon l'invention dans une position avancée,
  • La figure 4 est une vue similaire à celle de la figure 3, dans une position reculée,
  • La figure 5 est une vue similaire à celle de la figure 3, dans une position de décrochage,
  • La figure 6 est une vue similaire à celle de la figure 3, dans une position écartée,
  • La figure 7 est une vue en perspective du système de translation du capot mobile,
  • La figure 8 est une vue de face de la liaison entre le capot mobile et le système de translation, et
  • La figure 9 est une vue en perspective d'un système de translation motorisé.
The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
  • The figure 1 is a side view of an aircraft according to the invention,
  • The figure 2 is a schematic representation in front view of a propulsion system according to the invention,
  • The figure 3 is a side sectional view of a turbojet engine of the propulsion system according to the invention in an advanced position,
  • The figure 4 is a view similar to that of the figure 3 , in a remote position,
  • The figure 5 is a view similar to that of the figure 3 , in a stall position,
  • The figure 6 is a view similar to that of the figure 3 , in a spread position,
  • The figure 7 is a perspective view of the translation system of the movable cover,
  • The figure 8 is a front view of the connection between the movable cover and the translation system, and
  • The figure 9 is a perspective view of a motorized translation system.

Dans la description qui suit, les termes relatifs à une position sont pris en référence au sens d'avancement d'un aéronef.In the following description, the terms relating to a position are taken with reference to the direction of advance of an aircraft.

En relation avec la figure 1, un aéronef 10 comporte un fuselage 12 de chaque côté duquel est fixée une aile 14 qui porte au moins un système de propulsion 100 comportant un turboréacteur double flux 150 et un mât 152 qui assure la fixation du turboréacteur double flux 150 sous l'aile 14.In connection with the figure 1 , an aircraft 10 comprises a fuselage 12 on each side of which is fixed a wing 14 which carries at least one propulsion system 100 comprising a turbofan 150 and a mast 152 which secures the turbofan 150 under the wing 14 .

Dans la description qui suit, et par convention, on appelle X l'axe longitudinal du turboréacteur double flux 150 qui est parallèle à l'axe longitudinal de l'aéronef 10 et orienté positivement vers l'avant de l'aéronef 10, on appelle Y l'axe transversal qui est horizontal lorsque l'aéronef 10 est au sol, et Z l'axe vertical lorsque l'aéronef 10 est au sol, ces trois axes X, Y et Z étant orthogonaux entre eux.In the following description, and by convention, X is called the longitudinal axis of the turbofan 150 which is parallel to the longitudinal axis of the aircraft 10 and oriented positively towards the front of the aircraft 10, Y the transverse axis which is horizontal when the aircraft 10 is on the ground, and Z the vertical axis when the aircraft 10 is on the ground, these three axes X, Y and Z being orthogonal to one another.

La figure 2 montre schématiquement le système de propulsion 100 qui comporte le turboréacteur double flux 150 et le mât 152 et la figure 3 montre une vue schématique de côté du turboréacteur double flux 150.The figure 2 schematically shows the propulsion system 100 which comprises the turbofan 150 and the mast 152 and the figure 3 shows a schematic side view of the double-flow turbojet 150.

Le turboréacteur 150 comporte un moteur 156 avec une soufflante 151 destinée à générer un flux d'air dans le turboréacteur 150 selon une direction de déplacement 50 de l'air dans le turboréacteur 150, où de manière connue, le flux d'air se déplace ensuite en aval de la soufflante 151 pour partie dans une veine primaire 153 du turboréacteur 150 et pour partie dans une veine secondaire 154 du turboréacteur 150.The turbojet 150 comprises a motor 156 with a blower 151 intended to generate an air flow in the turbojet 150 in a direction of movement 50 of the air in the turbojet 150, where in known manner, the air flow moves then downstream of the fan 151 partly in a primary stream 153 of the turbojet 150 and partly in a secondary stream 154 of the turbojet 150.

Le moteur 156 forme un noyau à travers lequel circule l'air de la veine primaire 153 et comportant en série un compresseur moteur, une chambre de combustion et une turbine moteur. La soufflante 151 est à l'avant du moteur 156.The engine 156 forms a core through which the air from the primary stream 153 circulates and comprising in series an engine compressor, a combustion chamber and an engine turbine. The fan 151 is at the front of the engine 156.

Le moteur 156 est entouré d'une structure interne fixe 158 (également appelée IFS « Internai Fixed Structure » en Anglo-saxon) qui délimite intérieurement la veine secondaire 154. La structure interne fixe 158 est constituée de deux capots internes 159 disposés de part et d'autre du plan milieu XZ du turboréacteur 150. Chaque capot interne 159 comporte ici une partie centrale 159a prenant la forme d'un demi-cylindre dont l'axe est l'axe longitudinal X, et deux extensions 159b-c. Chaque extension 159b-c prend globalement la forme d'une plaque où chacune s'étend dans un plan globalement parallèle au plan milieu XZ. L'extension supérieure 159b s'étend vers le haut depuis le bord supérieur de la partie centrale 159a et l'extension inférieure 159c s'étend vers le bas depuis le bord inférieur de la partie centrale 159a.The motor 156 is surrounded by a fixed internal structure 158 (also called IFS “Internai Fixed Structure” in English) which internally delimits the secondary vein 154. The fixed internal structure 158 consists of two internal cowls 159 arranged on one side and on the other side of the mid-plane XZ of the turbojet engine 150. Each internal cover 159 here comprises a central part 159a taking the form of a half-cylinder whose axis is the longitudinal axis X, and two extensions 159b-c. Each 159b-c extension generally takes the form of a plate where each extends in a plane generally parallel to the middle plane XZ. The upper extension 159b extends upwards from the upper edge of the central part 159a and the lower extension 159c extends downwards from the lower edge of the central part 159a.

En position de fonctionnement du turboréacteur 150, la structure interne fixe 158, c'est-à-dire les capots internes 159, sont fixes par rapport au moteur 156, et en position de maintenance la structure interne fixe 158, c'est-à-dire les capots internes 159, sont libres par rapport au moteur 156. A cette fin, le turboréacteur 150 comporte des moyens de verrouillage 180 qui peuvent prendre alternativement une position de verrouillage dans laquelle ils verrouillent les capots internes 159 au moteur 156, et une position de déverrouillage dans laquelle ils libèrent les capots internes 159 du moteur 156.In the operating position of the turbojet engine 150, the fixed internal structure 158, that is to say the internal cowls 159, are fixed relative to the engine 156, and in the maintenance position the fixed internal structure 158, that is to say -to say the internal covers 159, are free with respect to the engine 156. To this end, the turbojet engine 150 comprises locking means 180 which can alternately take a locking position in which they lock the internal covers 159 to the engine 156, and a unlocking position in which they release the internal covers 159 of the motor 156.

Le turboréacteur 150 comporte également une nacelle 160 qui entoure la structure interne fixe 158 et qui comporte un carter de soufflante 162 autour de la soufflante 151 et deux capots extérieurs 164 disposés autour de la structure interne fixe 158, c'est-à-dire des capots internes 159. Les capots extérieurs 164 sont également disposés de part et d'autre du plan milieu XZ du turboréacteur 150. Chaque capot extérieur 164 se trouve autour de l'un des capots internes 159.The turbojet engine 150 also includes a nacelle 160 which surrounds the fixed internal structure 158 and which comprises a fan casing 162 around the fan 151 and two external covers 164 arranged around the fixed internal structure 158, that is to say internal covers 159. The external covers 164 are also arranged on either side of the middle plane XZ of the turbojet engine 150. Each external cover 164 is located around one of the internal covers 159.

Le carter de soufflante 162 est fixe et à l'avant de la nacelle 160 tandis que chaque capot extérieur 164 est à l'arrière du carter de soufflante 162 et est mobile en translation selon une direction de translation globalement parallèle à l'axe longitudinal X. Le carter de soufflante 162 est également constitué de deux capots de soufflante disposés de part et d'autre du plan milieu XZ du turboréacteur 150.The fan casing 162 is fixed and at the front of the nacelle 160 while each outer cover 164 is at the rear of the fan casing 162 and is movable in translation in a direction of translation generally parallel to the longitudinal axis X The fan casing 162 also consists of two fan cowls arranged on either side of the middle plane XZ of the turbojet engine 150.

La figure 3 montre le turboréacteur 150 avec les capots extérieurs 164 dans une position avancée, et la figure 4 montre le turboréacteur 150 avec les capots extérieurs 164 dans une position reculée. Les capots extérieurs 164 délimitent extérieurement la veine secondaire 154.The figure 3 shows the turbojet engine 150 with the outer covers 164 in a forward position, and the figure 4 shows the turbojet 150 with the outer covers 164 in a retracted position. The outer covers 164 externally delimit the secondary vein 154.

Chaque capot extérieur 164 est monté coulissant parallèlement à la direction de translation sur le capot interne 159 correspondant par l'intermédiaire d'une liaison glissière haute 170 et d'une liaison glissière basse 172. La liaison glissière haute 170 est arrangée en partie haute du turboréacteur 150 et la liaison glissière basse 172 est arrangée en partie basse du turboréacteur 150.Each outer cover 164 is slidably mounted parallel to the direction of translation on the corresponding inner cover 159 by means of a high slide link 170 and a low slide link 172. The high slide link 170 is arranged in the upper part of the turbojet 150 and the lower slide link 172 is arranged in the lower part of turbojet 150.

La liaison glissière haute 170 et la liaison glissière basse 172 sont réalisées par tous moyens appropriés comme par exemple une rainure dans l'un parmi le capot extérieur 164 ou le capot interne 159 et un coulisseau solidaire de l'autre parmi le capot interne 159 ou le capot extérieur 164 et qui coulisse dans la rainure. Dans le mode de réalisation de l'invention proposé ici, la liaison glissière haute 170 et la liaison glissière basse 172 sont plus particulièrement mises en œuvre au niveau de l'extension supérieure 159b et de l'extension inférieure 159c.The upper slide link 170 and the low slide link 172 are produced by any suitable means such as for example a groove in one of the external cover 164 or the internal cover 159 and a slide integral with the other among the internal cover 159 or the outer cover 164 and which slides in the groove. In the embodiment of the invention proposed here, the upper slide link 170 and the low slide link 172 are more particularly implemented at the upper extension 159b and the lower extension 159c.

Chaque capot extérieur 164 est également monté coulissant parallèlement à la direction de translation sur le mât 152 par l'intermédiaire d'une liaison glissière supérieure 174 disposée également en partie haute du turboréacteur 150.Each outer cover 164 is also slidably mounted parallel to the direction of translation on the mast 152 by means of an upper slide link 174 also arranged in the upper part of the turbojet engine 150.

La liaison glissière supérieure 174 comporte, d'une part, une poutre 176 présentant une rainure et, d'autre part, au moins un coulisseau solidaire du capot extérieur 164 qui coulisse dans la rainure.The upper slide link 174 comprises, on the one hand, a beam 176 having a groove and, on the other hand, at least one slide secured to the outer cover 164 which slides in the groove.

La poutre 176 est fixée au mât 152 par l'intermédiaire d'une liaison pivot autour d'un axe de rotation 177 globalement parallèle à la direction de translation et donc ici à l'axe longitudinal X, formant ainsi une charnière permettant le déplacement du capot extérieur 164 entre une position fermée dans laquelle le capot extérieur 164 est resserré autour du moteur 156 et une position ouverte dans laquelle le capot extérieur 164 est écarté du moteur 156 en entraînant le capot interne 159 correspondant.The beam 176 is fixed to the mast 152 by means of a pivot link around an axis of rotation 177 generally parallel to the direction of translation and therefore here to the longitudinal axis X, thus forming a hinge allowing the movement of the outer cover 164 between a closed position in which the outer cover 164 is tightened around the motor 156 and an open position in which the outer cover 164 is moved away from the motor 156 by driving the corresponding inner cover 159.

En position fermée, les deux capots extérieurs 164 sont resserrés pour former une continuité aérodynamique avec le carter de soufflante 162.In the closed position, the two outer covers 164 are tightened to form an aerodynamic continuity with the fan casing 162.

Le turboréacteur 150 comporte également un système inverseur 250.The turbojet 150 also includes an inverter system 250.

Le système inverseur 250 comporte les capots extérieurs 164 qui sont mobiles en translation par rapport au moteur 156 entre une position avancée et une position reculée. En position avancée, les capots extérieurs 164 sont accolés à l'arrière du carter de soufflante 162 et en position reculée, les deux capots extérieurs 164 sont à distance du carter de soufflante 162 pour ouvrir une fenêtre 252 entre la veine secondaire 154 et l'extérieur. La fenêtre 252 est délimitée à l'avant par le carter de soufflante 162 et à l'arrière par les capots extérieurs 164 comme cela est visible sur la figure 4.The reversing system 250 comprises the outer covers 164 which are movable in translation relative to the motor 156 between an advanced position and a retracted position. In the advanced position, the outer covers 164 are attached to the rear of the fan casing 162 and in the retracted position, the two outer covers 164 are spaced from the fan casing 162 to open a window 252 between the secondary stream 154 and the outside. The window 252 is delimited at the front by the fan casing 162 and at the rear by the external covers 164 as can be seen on the figure 4 .

Pour déplacer chaque capot extérieur 164 de la position avancée à la position reculée, le turboréacteur 150 comporte un premier système de transmission mécanique qui comprend par exemple des actionneurs tels que des vérins, des moteurs, des crémaillères et qui est commandé par une unité de contrôle de l'aéronef 10. Pour assurer un bon déplacement du capot extérieur 164, il est préférable de prévoir un premier système de transmission mécanique au niveau de la liaison glissière basse 172 et un au niveau de la liaison glissière supérieure 174.To move each outer cover 164 from the advanced position to the retracted position, the turbojet engine 150 comprises a first mechanical transmission system which includes, for example actuators such as jacks, motors, racks and which is controlled by a control unit of the aircraft 10. To ensure proper movement of the outer cover 164, it is preferable to provide a first mechanical transmission system at the level of the lower slide link 172 and one at the level of the upper slide link 174.

Pour chaque capot extérieur 164, le système inverseur 250 comporte également au moins une porte 254 qui est montée mobile en rotation sur le capot extérieur 164 autour d'un axe globalement perpendiculaire à l'axe longitudinal X.For each outer cover 164, the reversing system 250 also includes at least one door 254 which is mounted to rotate on the outer cover 164 around an axis generally perpendicular to the longitudinal axis X.

Chaque porte 254 est mobile entre une position escamotée et une position déployée. En position escamotée (figure 3), la porte 254 n'est pas en travers de la veine secondaire 154 et ne fait donc pas obstacle au passage du flux d'air dans la veine secondaire 154. En position déployée (figure 4), la porte 254 est en travers de la veine secondaire 154 de manière à dévier le flux d'air vers la fenêtre 252. Ici, en position déployée, la porte 254 vient contre le capot interne 159.Each door 254 is movable between a retracted position and a deployed position. In the retracted position ( figure 3 ), the door 254 is not across the secondary stream 154 and therefore does not obstruct the passage of the air flow in the secondary stream 154. In the deployed position ( figure 4 ), the door 254 is across the secondary stream 154 so as to divert the air flow towards the window 252. Here, in the deployed position, the door 254 comes against the internal cover 159.

Pour chaque porte 254, le système inverseur 250 comporte également un deuxième système de transmission mécanique 256 qui permet de déplacer la porte 254 de la position escamotée à la position déployée lorsque le capot extérieur 164 passe de la position avancée à la position reculée. Ici, le deuxième système de transmission mécanique 256 est une tringle fixée entre la porte 254 et la structure interne fixe 158, mais il pourrait comprendre par exemple des actionneurs tels que des vérins, des moteurs commandés par l'unité de contrôle.For each door 254, the reversing system 250 also includes a second mechanical transmission system 256 which makes it possible to move the door 254 from the retracted position to the deployed position when the outer cover 164 changes from the advanced position to the retracted position. Here, the second mechanical transmission system 256 is a rod fixed between the door 254 and the fixed internal structure 158, but it could for example include actuators such as jacks, motors controlled by the control unit.

Pour augmenter la déviation du flux d'air sortant par la fenêtre 252, le turboréacteur 150 comporte des cascades 256 qui sont fixées au capot extérieur 164 par l'intermédiaire de moyens de ceinturage 258 qui peuvent prendre alternativement une position de ceinturage dans laquelle ils verrouillent les cascades 256 au capot extérieur 164, et une position de désengagement dans laquelle ils libèrent les cascades 256 du capot extérieur 164.To increase the deflection of the air flow exiting through the window 252, the turbojet engine 150 comprises cascades 256 which are fixed to the outer cover 164 by means of belt means 258 which can alternately assume a belt position in which they lock the cascades 256 to the outer cover 164, and a disengagement position in which they release the cascades 256 from the outer cover 164.

En position avancée, les cascades 256 se positionnent sous le carter de soufflante 162 et en position reculée, les cascades 256 se positionnent en travers de la fenêtre 252.In the advanced position, the cascades 256 are positioned under the fan casing 162 and in the retracted position, the cascades 256 are positioned across the window 252.

Le déplacement en translation des cascades 256 entre la position avancée et la position reculée est également assuré par la liaison glissière supérieure 174, où les cascades 256 comportent au moins un coulisseau qui coulisse dans la rainure de la poutre 176.The displacement in translation of the cascades 256 between the advanced position and the retracted position is also ensured by the upper slide link 174, where the cascades 256 comprise at least one slide which slides in the groove of the beam 176.

Ainsi en position de fonctionnement, lorsque le système inverseur 250 est activé, les capots extérieurs 164 et les cascades 256 sont déplacés vers la position reculée le long de la liaison glissière haute 170, de la liaison glissière basse 172 et de la liaison glissière supérieure 174, entraînant le déplacement de chaque porte 254 vers la position déployée, tandis que les capots internes 159 restent fixes.Thus in the operating position, when the reversing system 250 is activated, the outer covers 164 and the cascades 256 are moved to the retracted position along the upper slide link 170, the low slide link 172 and the upper slide link 174 , causing each door 254 to move to the deployed position, while the internal covers 159 remain fixed.

Les figures 5 et 6 correspondent aux phases de maintenance du turboréacteur 150. A partir de la position avancée (figure 5), les moyens de verrouillage 180 sont déverrouillés et les moyens de ceinturage 258 sont désengagés, c'est-à-dire que les capots internes 159 sont libérés du moteur 156 et que les cascades 256 sont libérées du capot extérieur 164.The Figures 5 and 6 correspond to the maintenance phases of the turbojet 150. From the advanced position ( figure 5 ), the locking means 180 are unlocked and the belt means 258 are disengaged, that is to say that the internal covers 159 are released from the motor 156 and that the cascades 256 are released from the external cover 164.

En passant les capots extérieurs 164 de la position avancée à la position reculée (figure 6), les capots internes 159 se déplacent également vers l'arrière tandis que les cascades 256 restent sous le carter de soufflante 162. Ceci permet de libérer l'accès au moteur 156 sans qu'il soit nécessaire de déposer les différents capots 159 et 164.By passing the outer covers 164 from the advanced position to the retracted position ( figure 6 ), the internal covers 159 also move backwards while the cascades 256 remain under the fan casing 162. This makes it possible to free access to the engine 156 without it being necessary to remove the various covers 159 and 164 .

Chaque capot de soufflante est également ici fixé au mât 152 par l'intermédiaire d'une liaison pivot autour de l'axe de rotation 177. La liaison pivot est réalisée par tous moyens appropriés comme par exemple des charnières.Each fan cover is also here attached to the mast 152 by means of a pivot connection around the axis of rotation 177. The pivot connection is produced by any suitable means such as for example hinges.

Dans le mode de réalisation de l'invention présenté ici, les moyens de verrouillage 180 comportent, d'une part, une rainure qui est ouverte vers l'extérieur, c'est-à-dire radialement par rapport à l'axe longitudinal et la direction de translation, qui s'étend autour du moteur 156 et qui en est solidaire, et, d'autre part, pour chaque capot interne 159, une nervure solidaire du capot interne 159 qui loge dans la rainure en position de verrouillage et en sort en position de déverrouillage. En position de verrouillage des moyens de verrouillage 180, la nervure qui est dans la rainure empêche le déplacement des capots internes 159 parallèlement à la direction de translation. La sortie de la nervure de la rainure est réalisée par un soulèvement de la nervure par rapport à la rainure.In the embodiment of the invention presented here, the locking means 180 comprise, on the one hand, a groove which is open towards the outside, that is to say radially with respect to the longitudinal axis and the direction of translation, which extends around the motor 156 and which is integral therewith, and, on the other hand, for each internal cover 159, a rib secured to the internal cover 159 which accommodates in the groove in the locked position and in comes out in unlocked position. In the locking position of the locking means 180, the rib which is in the groove prevents the displacement of the internal covers 159 parallel to the direction of translation. The exit of the rib from the groove is achieved by lifting the rib relative to the groove.

Dans le mode de réalisation de l'invention présenté ici, les moyens de ceinturage 258 comportent, d'une part, une rainure qui est ouverte vers l'extérieur, c'est-à-dire radialement par rapport à l'axe longitudinal et la direction de translation, qui s'étend autour du moteur 156 et qui est solidaire du capot extérieur 164, et, d'autre part, pour chaque cascade 256, une nervure solidaire de la cascade 256 qui loge dans la rainure en position de ceinturage et en sort en position de désengagement. En position de ceinturage des moyens de ceinturage 258, la nervure qui est dans la rainure, permet de solidariser la cascade 256 et le capot extérieur 164 pour assurer les déplacements parallèlement à la direction de translation. La sortie de la nervure de la rainure est réalisée par un abaissement de la rainure vers le moteur 156 par rapport à la nervure.In the embodiment of the invention presented here, the belt means 258 comprise, on the one hand, a groove which is open towards the outside, that is to say radially with respect to the longitudinal axis and the direction of translation, which extends around the motor 156 and which is secured to the outer cover 164, and, on the other hand, for each cascade 256, a rib secured to the cascade 256 which lodges in the groove in the belt position and leaves it in the disengagement position. In the belt position of the belt means 258, the rib which is in the groove makes it possible to secure the cascade 256 and the outer cover 164 to ensure the movements parallel to the direction of translation. The exit of the rib from the groove is achieved by lowering the groove towards the motor 156 relative to the rib.

La figure 7 montre la poutre 176 montée sur le mât 152 avec sa rainure 702 et un coulisseau 704 du capot extérieur 164 qui coulisse dans la rainure 702 parallèlement à la direction de translation.The figure 7 shows the beam 176 mounted on the mast 152 with its groove 702 and a slide 704 of the outer cover 164 which slides in the groove 702 parallel to the direction of translation.

La figure 8 montre une vue de face de la poutre 176 où chaque coulisseau 704 du capot extérieur 164 présente un degré de liberté en translation parallèlement à la direction de translation, ainsi qu'un degré de liberté en rotation autour d'un axe de battement 802 parallèle à la direction de translation et différent de l'axe de rotation 177. C'est-à-dire qu'entre chaque coulisseau 704 du capot extérieur 164 et la rainure 702, il y a une liaison pivot glissant.The figure 8 shows a front view of the beam 176 where each slide 704 of the outer cover 164 has a degree of freedom in translation parallel to the direction of translation, as well as a degree of freedom in rotation about a flapping axis 802 parallel to the direction of translation and different from the axis of rotation 177. That is to say that between each slide 704 of the outer cover 164 and the groove 702, there is a sliding pivot connection.

Le débattement angulaire (double flèche 804) de la liaison pivot correspondante est limité, il est par exemple de l'ordre de +/- 4 degrés. Le débattement angulaire est suffisant pour permettre le désengagement des moyens de ceinturage 258 en sortant la nervure de la rainure.The angular movement (double arrow 804) of the corresponding pivot link is limited, it is for example of the order of +/- 4 degrees. The angular movement is sufficient to allow the disengagement of the belt means 258 by leaving the rib from the groove.

Le procédé pour placer le système de propulsion 100 en position de maintenance, c'est-à-dire pour déplacer le capot extérieur 164 et le capot interne 159 vers l'arrière pour laisser la place à un technicien intervenant sur le moteur 156 consiste d'abord à déverrouiller les premiers moyens de verrouillage 180 et les moyens de ceinturage 258.The method for placing the propulsion system 100 in the maintenance position, that is to say for moving the outer cover 164 and the inner cover 159 backwards to make room for a technician working on the engine 156 consists of: 'first to unlock the first locking means 180 and the belt means 258.

Le procédé consiste ainsi à :

  • déplacer le capot de soufflante et le capot extérieur 164 de la position fermée à la position ouverte par rotation autour de l'axe de rotation 177, ceci va entraîner le déplacement des cascades 256 et du capot interne 159, ce qui va entraîner le déverrouillage des moyens de verrouillage 180 par sortie de la nervure de la rainure,
  • déplacer le capot extérieur 164 autour de l'axe de battement 802 pour déloger la nervure de la cascade 256 de la rainure du capot extérieur 164 et ainsi entraîner le désengagement des moyens de ceinturage 258, ce déplacement consiste à rabattre légèrement le capot extérieur 164 vers le moteur 156 par rotation autour de l'axe de battement 802 dans le sens de la position ouverte vers la position fermée, et
  • déplacer vers l'arrière le capot extérieur 164 et le capot interne 159 tandis que les cascades 256 restent en position.
The process thus consists in:
  • move the fan cover and the outer cover 164 from the closed position to the open position by rotation around the axis of rotation 177, this will cause the cascades 256 and the internal cover 159 to move, which will cause the unlocking of the locking means 180 by exit from the rib of the groove,
  • move the outer cover 164 around the flap axis 802 to dislodge the rib of the cascade 256 from the groove of the outer cover 164 and thus cause the disengagement of the belt means 258, this displacement consists in slightly folding the outer cover 164 towards the motor 156 by rotation about the flap axis 802 in the direction from the open position to the closed position, and
  • move the outer cover 164 and the inner cover 159 backwards while the cascades 256 remain in position.

Ce procédé s'applique pour chaque côté du turboréacteur 150.This process applies to each side of the turbojet 150.

Dans le mode de réalisation de l'invention présenté à la figure 8, le coulisseau 704 présente une section en haricot et il est logé dans une rainure 702 présentant également une section en haricot mais avec des dimensions supérieures.In the embodiment of the invention presented in the figure 8 , the slide 704 has a bean section and it is housed in a groove 702 also having a bean section but with larger dimensions.

Le coulisseau 704 et la rainure 702 peuvent présenter d'autres formes de section comme par exemple une section circulaire. Il est suffisant que les dimensions de la rainure 702 soient supérieures aux dimensions du coulisseau 704 pour autoriser la rotation de la liaison pivot glissant.The slide 704 and the groove 702 can have other cross-sectional shapes such as for example a circular section. It is sufficient that the dimensions of the groove 702 are greater than the dimensions of the slider 704 to allow the rotation of the sliding pivot connection.

Dans le mode de réalisation de l'invention présenté à la figure 8, le fond de la rainure 702 est recouvert d'un profilé 806 en particulier métallique et plus particulièrement en aluminium. Ce profilé 806 permet d'améliorer le glissement du coulisseau 704 et de renforcer la poutre 176. La surface intérieure du profilé 806 en contact avec le coulisseau 806 peut être recouverte d'un revêtement glissant.In the embodiment of the invention presented in the figure 8 , the bottom of the groove 702 is covered with a profile 806 in particular metallic and more particularly aluminum. This profile 806 makes it possible to improve the sliding of the slide 704 and to reinforce the beam 176. The interior surface of the profile 806 in contact with the slide 806 can be covered with a sliding coating.

Comme expliqué ci-dessus, le premier système de transmission mécanique peut comprendre par exemple des actionneurs tels que des vérins, des moteurs...As explained above, the first mechanical transmission system can comprise, for example, actuators such as jacks, motors, etc.

La figure 9 montre un mode de réalisation particulier du premier système de transmission mécanique 900 qui est constitué d'un moteur électrique linéaire synchrone 902 et qui est mis en place au niveau de la liaison glissière supérieure 174. Un tel moteur électrique linéaire 902 peut également être mis en place au niveau de la liaison glissière basse 172 où la poutre constitue une partie du capot interne 159 et le coulisseau constitue une partie du capot extérieur 164.The figure 9 shows a particular embodiment of the first mechanical transmission system 900 which consists of a synchronous linear electric motor 902 and which is put in place at the level of the upper slide link 174. Such a linear electric motor 902 can also be implemented place at the level of the lower slide link 172 where the beam constitutes a part of the internal cover 159 and the slide constitutes a part of the external cover 164.

Chaque moteur électrique linéaire 902 comporte une première série de bobines 906a-c alignées les unes à la suite des autres selon la direction de translation.Each linear electric motor 902 comprises a first series of coils 906a-c aligned one after the other in the direction of translation.

Chaque moteur électrique linéaire 902 comporte une deuxième série de bobines 908a-c alignées les unes à la suite des autres selon la direction de translation.Each linear electric motor 902 comprises a second series of coils 908a-c aligned one after the other in the direction of translation.

Chaque bobine 908a-c de la deuxième série est en regard d'une bobine 906a-c de la première série.Each coil 908a-c of the second series is opposite a coil 906a-c of the first series.

Chaque poutre 176 comporte un évidement 901 qui s'étend parallèlement à la direction de translation et dans lequel sont logées la première série de bobines 906a-c et la deuxième série de bobines 908a-c.Each beam 176 has a recess 901 which extends parallel to the direction of translation and in which are housed the first series of coils 906a-c and the second series of coils 908a-c.

Chaque moteur électrique linéaire 902 comporte également une bande 904 qui est intégrée au coulisseau 704 et qui s'étend selon la direction de translation et qui est constituée d'une succession d'aimants permanents 910a-c alignés les uns à la suite des autres selon la direction de translation. Les aimants permanents 910a-c sont disposés entre la première série et la deuxième série de bobines 906a-c, 908a-c. Les aimants permanents 910a-c présentent leur pôle Nord alternativement vers la première série de bobines 906a-c et la deuxième série de bobines 908a-c. C'est-à-dire que lorsqu'un aimant permanent 910a-c présente son pôle Nord vers la première série 906a-c et son pôle Sud vers la deuxième série 908a-c, les deux aimants permanents 910a-c voisins présentent leurs pôles Nord vers la deuxième série 908a-c et leurs pôles Sud vers la première série 906a-c.Each linear electric motor 902 also comprises a strip 904 which is integrated into the slide 704 and which extends in the direction of translation and which consists of a succession of permanent magnets 910a-c aligned one after the other according to the direction of translation. Permanent magnets 910a-c are placed between the first series and the second series of coils 906a-c, 908a-c. The permanent magnets 910a-c present their North Pole alternately towards the first series of coils 906a-c and the second series of coils 908a-c. In other words, when a permanent magnet 910a-c has its North Pole towards the first series 906a-c and its South Pole towards the second series 908a-c, the two neighboring permanent magnets 910a-c have their poles North towards the second series 908a-c and their poles South towards the first series 906a-c.

Dans le mode de réalisation de l'invention présenté à la figure 9, pour chaque série de bobines 906a-c, 908a-c, les bobines de ladite série sont fixées sur une plaque support 914, 916 qui est disposée du côté opposé au coulisseau 704.In the embodiment of the invention presented in the figure 9 , for each series of coils 906a-c, 908a-c, the coils of said series are fixed on a support plate 914, 916 which is arranged on the side opposite to the slide 704.

Le principe consiste à alimenter les bobines 906a-c et 908a-c de chaque série qui sont en regard des aimants permanents 910a-c, en courant alternatif et déphasées judicieusement, afin de générer une force entraînant le déplacement du coulisseau 704. Deux bobines se faisant face (c'est-à-dire une bobine 906a-c de la première série face à une bobine 908a-c de la seconde série) sont alimentées de manière identique et donc calées de manière identique.The principle consists in supplying the coils 906a-c and 908a-c of each series which are opposite the permanent magnets 910a-c, with alternating current and judiciously phase-shifted, in order to generate a force causing the displacement of the slide 704. Two coils are facing (that is to say a coil 906a-c of the first series facing a coil 908a-c of the second series) are supplied in an identical manner and therefore calibrated in an identical manner.

A cette fin, chaque premier système de transmission mécanique 900 comporte un capteur de position 912 qui capte la position du coulisseau 704 le long de la direction de translation et donc la position des aimants permanents 910a-c par rapport aux bobines 906a-c, 908a-c. Le capteur de position 912 est par exemple un capteur magnétique qui détecte le changement de champ magnétique au passage des aimants permanents 910a-c et donc la distance parcourue par le coulisseau 704. A partir de l'information délivrée par le capteur de position 912, l'unité de contrôle détermine les bobines 906a-c, 908a-c qui sont en regard d'un aimant permanent 910a-c.To this end, each first mechanical transmission system 900 comprises a position sensor 912 which picks up the position of the slide 704 along the direction of translation and therefore the position of the permanent magnets 910a-c relative to the coils 906a-c, 908a -vs. The position sensor 912 is for example a magnetic sensor which detects the change of magnetic field when the permanent magnets 910a-c pass and therefore the distance traveled by the slide 704. From the information delivered by the position sensor 912, the control unit determines the coils 906a-c, 908a-c which are opposite a permanent magnet 910a-c.

Une alimentation électrique est prévue pour alimenter chaque bobine 906a-c, 908a-c et elle est commandée par l'unité de contrôle en fonction de l'information délivrée par le capteur de position 912 de manière à alimenter uniquement les bobines 906a-c, 908a-c qui sont en regard d'un aimant permanent 910a-c. L'alimentation sélective des bobines 906a-c, 908a-c permet de déplacer le coulisseau 704 le long de la direction de translation.An electrical supply is provided to supply each coil 906a-c, 908a-c and it is controlled by the control unit as a function of the information delivered by the position sensor 912 so as to supply only the coils 906a-c, 908a-c which are opposite a permanent magnet 910a-c. The selective supply of the coils 906a-c, 908a-c makes it possible to move the slider 704 along the direction of translation.

Chaque coulisseau 704 peut comporter une portion métallique (constituée d'une simple plaque conductrice ou de brins parallèles entre eux, disposés perpendiculairement à la trajectoire du coulisseau, et reliés aux extrémités) sans aimant dans le prolongement de la bande 904 pour bénéficier des courants de Foucault générés lors du déplacement du coulisseau 704 et assurer ainsi un freinage du coulisseau 704 en fin de course.Each slide 704 can comprise a metal portion (consisting of a simple conductive plate or of parallel strands between them, arranged perpendicular to the path of the slide, and connected to the ends) without a magnet in the extension of the strip 904 to benefit from the currents of Eddy generated during movement of the slide 704 and thus ensure braking of the slide 704 at the end of the stroke.

Le premier système de transmission mécanique 900 de la liaison glissière supérieure 174 comporte également un système de calage 950 qui peut prendre alternativement une position de calage dans laquelle le système de calage 950 bloque les deux séries de bobines 906a-c, 908a-c, empêchant tout mouvement desdites bobines 906a-c, 908a-c, et une position libre dans laquelle le système de calage 950 ne bloque pas les deux séries de bobines 906a-c, 908a-c, autorisant un mouvement rotatif desdites bobines 906a-c, 908a-c autour de l'axe de battement 802. Ce système de calage 950 permet ainsi de libérer le mouvement du capot extérieur 164 autour de l'axe de battement 802.The first mechanical transmission system 900 of the upper slide link 174 also includes a wedging system 950 which can alternately assume a wedging position in which the wedging system 950 blocks the two sets of coils 906a-c, 908a-c, preventing any movement of said coils 906a-c, 908a-c, and a free position in which the timing system 950 does not block the two series of coils 906a-c, 908a-c, allowing a rotary movement of said coils 906a-c, 908a -c around the axis of flap 802. This wedging system 950 thus makes it possible to release the movement of the outer cover 164 around the flap axis 802.

Dans le mode de réalisation de l'invention présenté à la figure 9, le système de calage 950 comporte des patins déformables 952 ici au nombre de deux, par exemple en élastomère, et disposés entre une série de bobines, ici la deuxième série de bobines 908a-c, et la poutre 176. Dans le mode de réalisation de l'invention présenté ici, les patins déformables 952 sont plus précisément disposés entre la plaque support 916 et la poutre 176.In the embodiment of the invention presented in the figure 9 , the wedging system 950 comprises deformable pads 952 here two in number, for example made of elastomer, and arranged between a series of coils, here the second series of coils 908a-c, and the beam 176. In the embodiment of the invention presented here, the deformable pads 952 are more precisely arranged between the support plate 916 and the beam 176.

Le système de calage 950 comporte également des moyens de mise en pression 954 qui sont disposés à l'opposé des patins déformables 952 contre l'autre série de bobines, ici la première série de bobines 906a-c. Les moyens de mise en pression 954 peuvent prendre alternativement une position de pression dans laquelle ils appuient sur ladite autre série de bobines, pour écraser les patins déformables 952, ou une position de relâche dans laquelle ils n'appuient pas sur ladite autre série de bobines, de manière à relâcher les patins déformables 952.The timing system 950 also includes pressurizing means 954 which are arranged opposite the deformable pads 952 against the other series of coils, here the first series of coils 906a-c. The pressurizing means 954 can alternately take a pressure position in which they press on said other series of coils, to crush the deformable pads 952, or a release position in which they do not press on said other series of coils , so as to release the deformable pads 952.

Les moyens de mise en pression 954 peuvent être par exemple des vis de serrage ou des électro-actuateurs comme des électroaimants, des vérins...The pressurizing means 954 may for example be clamping screws or electro-actuators such as electromagnets, jacks, etc.

Le moteur électrique synchrone peut être remplacé par un moteur asynchrone.The synchronous electric motor can be replaced by an asynchronous motor.

L'orientation de la direction de translation dépendra de l'encombrement autour du système de propulsion 100. Par exemple, la direction de translation pourra présenter un angle voisin de 90° par rapport à l'axe vertical Z pour garder le carter de soufflante 162 et le capot extérieur 164 alignés en position reculée. Par exemple, la direction de translation pourra présenter un angle voisin de 90° par rapport à l'axe transversal Y pour échapper à la voilure de l'aéronef 10 lors du déploiement.The orientation of the direction of translation will depend on the size around the propulsion system 100. For example, the direction of translation may have an angle close to 90 ° relative to the vertical axis Z to keep the fan casing 162 and the outer cover 164 aligned in the retracted position. For example, the direction of translation could have an angle close to 90 ° relative to the transverse axis Y to escape the wing of the aircraft 10 during deployment.

Selon un exemple, l'unité de contrôle comprend, reliés par un bus de communication: un processeur ou CPU (« Central Processing Unit » en anglais) ; une mémoire vive RAM (« Random Access Memory » en anglais) ; une mémoire morte ROM (« Read Only Memory » en anglais) ; une unité de stockage telle qu'un disque dur ou un lecteur de support de stockage, tel qu'un lecteur de cartes SD (« Secure Digital » en anglais) ; au moins une interface de communication, permettant par exemple à l'unité de contrôle de communiquer avec l'alimentation électrique, le capteur de position 912, les systèmes de transmission mécanique.According to one example, the control unit comprises, connected by a communication bus: a processor or CPU (“Central Processing Unit” in English); a random access memory RAM (“Random Access Memory” in English); a read only memory (ROM); a storage unit such as a hard disk or a storage medium reader, such as an SD card reader (“Secure Digital” in English); at least one communication interface, allowing for example the control unit to communicate with the power supply, the position sensor 912, the mechanical transmission systems.

Le processeur est capable d'exécuter des instructions chargées dans la RAM à partir de la ROM, d'une mémoire externe (non représentée), d'un support de stockage (tel qu'une carte SD), ou d'un réseau de communication. Lorsque l'équipement est mis sous tension, le processeur est capable de lire de la RAM des instructions et de les exécuter. Ces instructions forment un programme d'ordinateur causant la mise en œuvre, par le processeur, de tout ou partie des algorithmes et étapes décrits ci-dessus.The processor is capable of executing instructions loaded into RAM from the ROM, an external memory (not shown), a storage medium (such as an SD card), or a network of communication. When the equipment is powered up, the processor is able to read and execute instructions from RAM. These instructions form a computer program causing the processor to implement all or part of the algorithms and steps described above.

Tout ou partie des algorithmes et étapes décrits ci-après peut être implémenté sous forme logicielle par exécution d'un ensemble d'instructions par une machine programmable, par exemple un DSP (« Digital Signal Processor » en anglais) ou un microcontrôleur, ou être implémenté sous forme matérielle par une machine ou un composant dédié, par exemple un FPGA (« Field-Programmable Gate Array » en anglais) ou un ASIC (« Application-Specific Integrated Circuit » en anglais).All or part of the algorithms and steps described below can be implemented in software form by execution of a set of instructions by a programmable machine, for example a DSP (“Digital Signal Processor” in English) or a microcontroller, or be implemented in hardware form by a dedicated machine or component, for example an FPGA ("Field-Programmable Gate Array" in English) or an ASIC ("Application-Specific Integrated Circuit" in English).

Claims (7)

Système de propulsion (100) d'un aéronef (10) comportant un turboréacteur double flux (150) et un mât (152), où le turboréacteur double flux (150) comporte un moteur (156) avec une soufflante (151), deux capots internes (159) entourant le moteur (156), un carter de soufflante (162) et deux capots extérieurs (164) entourant les capots internes (159) pour définir une veine secondaire (154) et disposés à l'arrière du carter de soufflante (162),
où le turboréacteur (150) comporte des moyens de verrouillage (180) qui peuvent prendre alternativement une position de verrouillage dans laquelle ils verrouillent les capots internes (159) du moteur (156), et une position de déverrouillage dans laquelle ils libèrent les capots internes (159) du moteur (156),
où les capots extérieurs (164) sont mobiles en translation par rapport au moteur (156) entre une position avancée dans laquelle les capots extérieurs (164) sont accolés à l'arrière du carter de soufflante (162) et une position reculée dans laquelle les deux capots extérieurs (164) sont à distance du carter de soufflante (162) pour ouvrir une fenêtre (252) entre la veine secondaire (154) et l'extérieur,
où le turboréacteur double flux (150) comporte en outre, pour chaque capot extérieur (164), au moins une porte (254) montée mobile en rotation sur le capot extérieur (164) entre une position escamotée dans laquelle la porte (254) n'est pas en travers de la veine secondaire (154) et une position déployée dans laquelle la porte (254) est en travers de la veine secondaire (154) pour dévier le flux d'air vers la fenêtre (252),
où le turboréacteur double flux (150) comporte en outre, des cascades (256) qui sont fixées au capot extérieur (164) par l'intermédiaire de moyens de ceinturage (258) qui peuvent prendre alternativement une position de ceinturage dans laquelle ils verrouillent les cascades (256) au capot extérieur (164), et une position de désengagement dans laquelle ils libèrent les cascades (256) du capot extérieur (164),
où chaque capot extérieur (164) est monté coulissant parallèlement à une direction de translation sur le capot interne (159) correspondant et où chaque capot extérieur (164) est monté coulissant parallèlement à la direction de translation sur le mât (152),
caractérisé en ce que
le turboréacteur (150) comporte des moyens de verrouillage (180) qui peuvent prendre alternativement une position de verrouillage dans laquelle ils verrouillent les capots internes (159) du moteur (156), et une position de déverrouillage dans laquelle ils libèrent les capots internes (159) du moteur (156),
et en ce que chaque capot extérieur (164) est monté coulissant sur le capot interne (159) correspondant par l'intermédiaire d'une liaison glissière haute (170) et d'une liaison glissière basse (172) et sur le mât (152) par l'intermédiaire d'une liaison glissière supérieure (174)
et en ce que où la liaison glissière supérieure (174) comporte, d'une part, une poutre (176) présentant une rainure et, d'autre part, au moins un coulisseau (704) solidaire du capot extérieur (164) qui coulisse dans la rainure et au moins un coulisseau solidaire des cascades (256) qui coulisse dans la rainure, où la poutre (176) est fixée au mât (152) par l'intermédiaire d'une liaison pivot autour d'un axe de rotation (177) parallèle à la direction de translation permettant le déplacement du capot extérieur (164) entre une position fermée dans laquelle le capot extérieur (164) est resserré autour du moteur (156) et une position ouverte dans laquelle le capot extérieur (164) est écarté du moteur (156).Propulsion system (100) of an aircraft (10) comprising a turbofan engine (150) and a mast (152), where the turbofan engine (150) comprises an engine (156) with a fan (151), two internal covers (159) surrounding the engine (156), a fan casing (162) and two external covers (164) surrounding the internal covers (159) to define a secondary stream (154) and arranged at the rear of the blower (162),
where the turbojet engine (150) comprises locking means (180) which can alternately take a locking position in which they lock the internal cowls (159) of the engine (156), and an unlocking position in which they release the internal cowls (159) of the engine (156),
wherein the outer covers (164) are movable in translation relative to the motor (156) between an advanced position in which the outer covers (164) are attached to the rear of the fan casing (162) and a retracted position in which the two outer covers (164) are spaced from the fan casing (162) to open a window (252) between the secondary stream (154) and the outside,
where the turbofan (150) further comprises, for each outer cover (164), at least one door (254) rotatably mounted on the outer cover (164) between a retracted position in which the door (254) n is not across the secondary stream (154) and a deployed position in which the door (254) is across the secondary stream (154) to divert the air flow towards the window (252),
where the turbofan (150) further comprises cascades (256) which are fixed to the outer cover (164) by means of belt (258) which can alternately assume a belt position in which they lock the cascades (256) to the external cover (164), and a disengagement position in which they release the cascades (256) from the external cover (164),
where each outer cover (164) is slidably mounted parallel to a direction of translation on the corresponding inner cover (159) and where each outer cover (164) is slidably mounted parallel to the direction of translation on the mast (152),
characterized in that
the turbojet engine (150) comprises locking means (180) which can alternately take a locking position in which they lock the internal cowls (159) of the engine (156), and an unlocking position in which they release the internal cowls ( 159) of the engine (156),
and in that each outer cover (164) is slidably mounted on the corresponding inner cover (159) by means of a high slide link (170) and a low slide link (172) and on the mast (152 ) via an upper slide link (174)
and in that where the upper slide connection (174) comprises, on the one hand, a beam (176) having a groove and, on the other hand, at least one slide (704) integral with the outer cover (164) which slides in the groove and at least one slide integral with the waterfalls (256) which slides in the groove, where the beam (176) is fixed to the mast (152) by means of a pivot connection around an axis of rotation ( 177) parallel to the direction of translation allowing the movement of the outer cover (164) between a closed position in which the outer cover (164) is tightened around the motor (156) and an open position in which the outer cover (164) is away from the engine (156). Système de propulsion (100) selon la revendication 1, caractérisé en ce que le carter de soufflante (162) est constitué de deux capots de soufflante, chacun étant fixé au mât (152) par l'intermédiaire d'une liaison pivot autour de l'axe de rotation (177) permettant le déplacement de chaque capot de soufflante entre la position fermée et la position ouverte, en ce que les moyens de verrouillage (180) comportent, d'une part, une rainure qui est ouverte vers l'extérieur, qui s'étend autour du moteur (156) et qui en est solidaire, et, d'autre part, pour chaque capot interne (159), une nervure solidaire du capot interne (159) qui loge dans la rainure en position de verrouillage et en sort en position de déverrouillage, en ce que les moyens de ceinturage (258) comportent, d'une part, une rainure qui est ouverte vers l'extérieur, qui s'étend autour du moteur (156) et qui est solidaire du capot extérieur (164), et, d'autre part, pour chaque cascade (256), une nervure solidaire de la cascade (256) qui loge dans la rainure en position de ceinturage et en sort en position de désengagement, et en ce que la liaison entre chaque coulisseau (704) du capot extérieur (164) et la rainure (702) est une liaison pivot glissant.Propulsion system (100) according to claim 1, characterized in that the fan casing (162) consists of two fan cowls, each one fixed to the mast (152) by means of a pivot connection around the axis of rotation (177) allowing the movement of each fan cover between the closed position and the open position, in that the locking means (180) comprise, on the one hand, a groove which is open towards the outside , which extends around the motor (156) and which is integral therewith, and, on the other hand, for each internal hood (159), a rib integral with the internal hood (159) which lodges in the groove in the locked position and leaves it in the unlocked position, in that the belt means (258) comprise, on the one hand, a groove which is open towards the outside, which extends around the motor (156) and which is integral with the outer cover (164), and, on the other hand, for each cascade (256), a rib secured to the cascade (2 56) which is housed in the groove in the belt position and leaves it in the disengaged position, and in that the connection between each slide (704) of the outer cover (164) and the groove (702) is a sliding pivot connection. Système de propulsion (100) selon l'une des revendications 1 ou 2, caractérisé en ce qu'il comporte un premier système de transmission mécanique (900) au niveau de la liaison glissière supérieure (174) et un premier système de transmission mécanique (900) au niveau de la liaison glissière basse (172) avec une poutre constituant une partie du capot interne (159) et un coulisseau constituant une partie du capot extérieur (164).Propulsion system (100) according to one of Claims 1 or 2, characterized in that it comprises a first mechanical transmission system (900) at the level of the upper slide link (174) and a first mechanical transmission system ( 900) at the level of the bottom slide connection (172) with a beam constituting a part of the internal cover (159) and a slide constituting a part of the external cover (164). Système de propulsion (100) selon la revendication 3, caractérisé en ce que la poutre (176) de la liaison glissière supérieure (174) et la poutre de la liaison glissière basse (172) comportent chacune un évidement (901) qui s'étend parallèlement à la direction de translation, en ce que chaque premier système de transmission mécanique (900) comporte : - une première série de bobines (906a-c) alignées les unes à la suite des autres selon la direction de translation, - une deuxième série de bobines (908a-c) alignées les unes à la suite des autres selon la direction de translation, où la première série de bobines (906a-c) et la deuxième série de bobines (908a-c) sont logées dans l'évidement (901), - une bande (904) qui est intégrée au coulisseau (704), qui s'étend selon la direction de translation et qui est constituée d'une succession d'aimants permanents (910a-c) alignés les uns à la suite des autres selon la direction de translation, où les aimants permanents (910a-c) sont disposés entre la première série et la deuxième série de bobines (906a-c, 908a-c), où deux aimants permanents (910a-c) consécutifs présentent leur pôle Nord alternativement vers la première série de bobines (906a-c) et la deuxième série de bobines (908a-c), - un capteur de position (912) configuré pour capter la position du coulisseau (704) le long de la direction de translation, - une alimentation électrique pour alimenter les bobines (906a-c, 908a-c), et - une unité de contrôle configurée pour commander l'alimentation électrique en fonction de l'information délivrée par le capteur de position (912) de manière à alimenter uniquement les bobines (906a-c, 908a-c) qui sont en regard d'un aimant permanent (910a-c), et en ce que le premier système de transmission mécanique (900) de la liaison glissière supérieure (174) comporte un système de calage (950) qui peut prendre alternativement une position de calage dans laquelle le système de calage (950) bloque les deux séries de bobines (906a-c, 908a-c), et une position libre dans laquelle le système de calage (950) ne bloque pas les deux séries de bobines (906a-c, 908a-c).Propulsion system (100) according to claim 3, characterized in that the beam (176) of the upper slide link (174) and the beam of the bottom slide link (172) each have a recess (901) which extends parallel to the direction of translation, in that each first mechanical transmission system (900) comprises: a first series of coils (906a-c) aligned one after the other in the direction of translation, - a second series of coils (908a-c) aligned one after the other in the direction of translation, where the first series of coils (906a-c) and the second series of coils (908a-c) are housed in the recess (901), - A strip (904) which is integrated into the slide (704), which extends in the direction of translation and which consists of a succession of permanent magnets (910a-c) aligned one after the other according to the direction of translation, where the permanent magnets (910a-c) are arranged between the first series and the second series of coils (906a-c, 908a-c), where two consecutive permanent magnets (910a-c) have their North Pole alternately to the first series of coils (906a-c) and the second series of coils (908a-c), a position sensor (912) configured to pick up the position of the slide (704) along the direction of translation, - a power supply to power the coils (906a-c, 908a-c), and - a control unit configured to control the electrical supply as a function of the information supplied by the position sensor (912) so as to supply only the coils (906a-c, 908a-c) which are opposite a permanent magnet (910a-c), and in that the first mechanical transmission system (900) of the upper slide link (174) comprises a wedging system (950) which can alternately assume a wedging position in which the wedging system (950) blocks the two series of coils (906a -c, 908a-c), and a free position in which the timing system (950) does not block the two series of coils (906a-c, 908a-c). Système de propulsion (100) selon la revendication 4, caractérisé en ce que le système de calage (950) comporte des patins déformables (952) disposés entre une série de bobines et la poutre (176), et des moyens de mise en pression (954) disposés à l'opposé des patins déformables (952) contre l'autre série de bobines et pouvant prendre alternativement une position de pression dans laquelle ils appuient sur ladite autre série de bobines, pour écraser les patins déformables (952), ou une position de relâche dans laquelle ils n'appuient pas sur ladite autre série de bobines, de manière à relâcher les patins déformables (952).Propulsion system (100) according to claim 4, characterized in that the timing system (950) comprises deformable pads (952) disposed between a series of coils and the beam (176), and pressurizing means ( 954) arranged opposite the deformable pads (952) against the other series of coils and which can alternately assume a pressure position in which they press on said other series of coils, to crush the deformable pads (952), or a release position in which they do not press on said other series of coils, so as to release the deformable pads (952). Procédé pour placer le système de propulsion (100) de la revendication 2 en position de maintenance consistant à : - déplacer le capot de soufflante et le capot extérieur (164) de la position fermée à la position ouverte par rotation autour de l'axe de rotation (177), en entraînant les cascades (256) et le capot interne (159), et le déverrouillage des premiers moyens de verrouillage (180), - déplacer le capot extérieur (164) autour de l'axe de battement (802) pour déloger la nervure de la cascade (256) de la rainure du capot extérieur (164), et - déplacer vers l'arrière le capot extérieur (164) et le capot interne (159) tandis que les cascades (256) restent en position. Method for placing the propulsion system (100) of claim 2 in the maintenance position consisting of: - move the fan cover and the external cover (164) from the closed position to the open position by rotation around the axis of rotation (177), driving the cascades (256) and the internal cover (159), and unlocking the first locking means (180), - move the outer cover (164) around the flap axis (802) to dislodge the rib of the cascade (256) from the groove of the outer cover (164), and - Move the outer cover (164) and the inner cover (159) backwards while the cascades (256) remain in position. Aéronef (10) comportant au moins un système de propulsion (100) selon l'une des revendications précédentes.Aircraft (10) comprising at least one propulsion system (100) according to one of the preceding claims.
EP19203914.7A 2018-11-30 2019-10-17 Propulsion system of an aircraft comprising a movable and hinged cover Active EP3659923B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1872156A FR3089207A1 (en) 2018-11-30 2018-11-30 propulsion system of an aircraft comprising a movable and articulated hood

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EP3659923A1 true EP3659923A1 (en) 2020-06-03
EP3659923B1 EP3659923B1 (en) 2022-02-16

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EP (1) EP3659923B1 (en)
CN (1) CN111252257B (en)
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Also Published As

Publication number Publication date
CN111252257B (en) 2023-04-07
FR3089207A1 (en) 2020-06-05
CN111252257A (en) 2020-06-09
US20200182194A1 (en) 2020-06-11
US11187189B2 (en) 2021-11-30
EP3659923B1 (en) 2022-02-16

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